Equipment for treating an aircraft turbomachine component

An equipment for treating an annular component of an aircraft turbomachine with a treating medium, the equipment comprising:

• a support having an elongate shape along an axis (X), said support comprising, at a longitudinal end of the support, a mount configured to receive the annular component to be treated which extends around said axis;
• a cover configured to be mounted on said annular component and to cover at least one upstream end of this annular component, said cover comprising a wall with an orifice extending therethrough along the axis (X);
• a clamp passing through said orifice and extending parallel to said axis (X), said clamp comprising a first elongate element engaging the wall of the cover and having a first threaded portion extending along said axis (X), and a second elongate element coupled to the support and having a second threaded portion configured to engage the first threaded portion so that rotation of the first threaded portion relative to the second elongate element selectively provides a clamping force that removably attaches the cover to said support;
• and
• an annular masking gasket configured to mask said annular component, said annular masking gasket extending around the axis (X) and being configured so as to be interposed between the mount and a downstream end of the annular component such that said annular masking gasket contacts both said mount and said downstream end of the annular component when the annular component is mounted to the equipment, said annular masking gasket comprising an annular gorge configured so as to be a counter-form of the downstream end of said annular component,
• wherein said cover combined with said annular masking gasket define a treating area for the annular component, so that only said treating area is configured to be in contact with the treating medium.